CN219691649U - Servo mechanism self-locking device - Google Patents
Servo mechanism self-locking device Download PDFInfo
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- CN219691649U CN219691649U CN202321404717.3U CN202321404717U CN219691649U CN 219691649 U CN219691649 U CN 219691649U CN 202321404717 U CN202321404717 U CN 202321404717U CN 219691649 U CN219691649 U CN 219691649U
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- 230000007246 mechanism Effects 0.000 title claims abstract description 49
- 230000005540 biological transmission Effects 0.000 claims abstract description 41
- 230000009471 action Effects 0.000 claims abstract description 8
- 239000007921 spray Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000005484 gravity Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
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- 230000009286 beneficial effect Effects 0.000 description 1
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Abstract
The utility model discloses a servo mechanism self-locking device, which belongs to the field of aircraft attitude control and comprises a driving mechanism, an actuating support lug, a locking pin and an electromagnet assembly; the actuating mechanism comprises a transmission screw rod for transmission; one end of the transmission screw rod is in transmission connection with the driving mechanism and is driven by the driving mechanism to rotate; the other end of the transmission screw rod is rotationally connected with the actuating support lug; the transmission screw rod is provided with a locking groove matched with the locking pin; the locking pin is configured to extend into or out of the locking groove under the action of electromagnetic force generated by the electromagnet assembly. The utility model can effectively solve the locking problem of the servo mechanism during the transportation of the rocket and effectively avoid the damage of the servo mechanism actuator and the rocket engine during the horizontal transportation.
Description
Technical Field
The utility model relates to the field of attitude control of aircrafts, in particular to a servo mechanism self-locking device.
Background
Attitude control of modern rocket, missile, aircraft and other aircrafts relies on engine thrust vector control. The thrust vector control of the engine relies on a servo mechanism to push the spray pipe or the control surface to move, so that the attitude control of the engine is realized.
At present, the new generation of aircrafts such as rockets, missiles and the like in China are gradually changed from the traditional grading mode of grading assembly, grading test and grading transportation to the three-flat mode of integral horizontal assembly, integral horizontal test and integral horizontal transportation.
When the aircraft such as carrier rocket or guided missile is transported to a technical factory building or a launching base by an assembly factory building after assembly is completed, the aircraft is in a horizontal transportation state, and the engine spray pipe can swing up and down under the action of gravity, so that the telescopic action of the servo mechanism actuator is driven, the reliability of the servo mechanism actuator can be damaged, meanwhile, low-frequency resonance of an engine can be possibly generated, the rocket engine is damaged, and further the whole rocket is launched in a disfavored mode. The traditional electrohydraulic servo mechanism has a complex integral structure, and is difficult to lock by adopting a hydraulic lock and is suitable for locking in the horizontal state of the high-power servo mechanism. The current mainstream servo is electric servo, if the self-locking is designed on the motor, the motor structure will be bigger and the reliability will be reduced.
In view of the foregoing, it is necessary to provide a new solution to the above-mentioned problems.
Disclosure of Invention
In order to solve the technical problems, the utility model provides the servo mechanism self-locking device which can effectively solve the locking problem of a servo mechanism during rocket transportation and effectively avoid the damage of a servo mechanism actuator and a rocket engine in the horizontal transportation process.
A servo self-locking device comprising: the device comprises a driving mechanism, an actuating support lug, a locking pin and an electromagnet assembly; the actuating mechanism comprises a transmission screw rod for transmission; one end of the transmission screw rod is in transmission connection with the driving mechanism and is driven by the driving mechanism to rotate; the other end of the transmission screw rod is rotationally connected with the actuating support lug; the transmission screw rod is provided with a locking groove matched with the locking pin; the locking pin is configured to extend into or out of the locking groove under the action of electromagnetic force generated by the electromagnet assembly.
Preferably, the actuating mechanism further comprises a housing; the transmission screw rod and the locking pin are both arranged in the housing.
Preferably, the device further comprises a lead screw nut; the screw nut is in threaded connection with the transmission screw; the driving mechanism comprises a power output shaft; the screw nut is fixedly connected with the power output shaft.
Preferably, the screw nut further comprises a bearing for fixing the screw nut; the bearing sleeve is arranged on the periphery of the screw nut, the bearing inner ring is fixedly connected with the screw nut, and the bearing outer ring is fixedly connected with the housing.
Preferably, a connecting shaft is fixedly arranged at the end part of the transmission screw close to one end of the actuation support lug; the connecting shaft is rotationally connected with the actuating support lug; the rotation axis of the actuating support lug is collinear with the center of the transmission screw.
Preferably, the device further comprises an electric connector for connecting the electromagnet assembly and an on-arrow power supply.
Preferably, the device also comprises a fixed support lug for connecting the servo mechanism with the arrow body; the fixed support lugs are hinged with the arrow body through the fixed pin shafts.
Compared with the prior art, the utility model has at least the following beneficial effects:
1. the utility model effectively solves the locking problem of the servo mechanism during the transportation of the rocket and effectively avoids the damage of the servo mechanism actuator and the rocket engine during the horizontal transportation process.
2. The utility model can realize the locking and unlocking of the actuating mechanism in the servo mechanism by utilizing the matching of the locking pin and the electromagnet assembly, and has simple structure and good stability.
3. The utility model can effectively solve the problem of swing of the engine spray pipe caused by gravity in the horizontal transfer process of the rocket, improves the reliability of the rocket engine and further ensures the success rate of rocket launching.
Drawings
Some specific embodiments of the utility model will be described in detail hereinafter by way of example and not by way of limitation with reference to the accompanying drawings. The same reference numbers will be used throughout the drawings to refer to the same or like parts or portions. It will be appreciated by those skilled in the art that the drawings are not necessarily drawn to scale.
In the accompanying drawings:
FIG. 1 is a perspective view of a servo self-locking device of the present utility model;
FIG. 2 is a top view of the servo self-locking device of the present utility model;
fig. 3 is a cross-sectional view of the position A-A in fig. 2.
Wherein the above figures include the following reference numerals:
1. the electric connector comprises an electric connector body, wherein the electric connector body comprises an electric connector lug, an actuating pin, an actuating mechanism, a driving mechanism, an electromagnet assembly, a locking pin, a connecting shaft, a power output shaft and an electric power transmission shaft.
Detailed Description
In order to make the objects, technical solutions and advantages of the present utility model more apparent, the technical solutions of the present utility model will be clearly and completely described below with reference to specific embodiments of the present utility model and corresponding drawings. It will be apparent that the described embodiments are only some, but not all, embodiments of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
As shown in fig. 1 to 3, a servo self-locking device includes: the drive mechanism 5, the actuating mechanism 4, the actuating lug 2, the locking pin 9, the electromagnet assembly 8, the spindle nut 13 and the bearing 14 for fixing the spindle nut 13. The actuating mechanism 4 comprises a drive screw 12 for the drive. One end of the transmission screw rod 12 is in transmission connection with the driving mechanism 5, and is driven by the driving mechanism 5 to rotate, and the other end of the transmission screw rod 12 is in rotary connection with the actuating support lug 2. The driving screw 12 is provided with a locking groove matched with the locking pin 9, and the locking pin 9 is configured to extend into or extend out of the locking groove under the action of electromagnetic force generated by the electromagnet assembly 8.
Specifically, the actuating mechanism 4 further includes a housing 11 and a drive screw 12 disposed in the housing 11. The locking pin 9 is arranged in the housing 11, is in sliding connection with the housing 11 and corresponds to the position of the transmission screw 12, so that the locking pin 9 moves radially along the transmission screw 12 under the action of external force.
The drive mechanism 5 is preferably a servo motor, which comprises a power output shaft 15, and the lead screw nut 13 is fixedly connected with the power output shaft 15, so that the lead screw nut 13 can rotate under the drive of the power output shaft 15. Preferably, the drive screw 12 and the screw nut 13 are preferably ball screw assemblies. At the same time, the spindle nut 13 is screwed with the drive spindle 12. The outer circumference of the screw nut 13 is sleeved with a bearing 14. The inner ring of the bearing 14 is fixedly connected with the screw nut 13, and the outer ring is fixedly connected with the housing 11. The screw nut 13 drives the transmission screw 12 to rotate by the driving action of the power output shaft 15.
The end of the drive screw 12 near one end of the actuating lug 2 is fixedly provided with a connecting shaft 10. The connecting shaft 10 is rotatably connected with the actuating support lug 2, and the rotation axis of the actuating support lug 2 is collinear with the center of the transmission screw 12, so that the actuating support lug 2 moves along the axial direction of the transmission screw 12 under the driving of the transmission screw 12 without affecting the rotation of the transmission screw 12.
In addition, the servo mechanism self-locking device also comprises an electric connector 1 for connecting the electromagnet assembly 8 and an on-arrow power supply.
As an embodiment of the utility model, the servo mechanism self-locking device further comprises a fixing support lug 7 for connecting the servo mechanism with the arrow body, and the fixing support lug 7 is hinged with the arrow body through a fixing pin shaft 6.
When the power supply is used, the power supply on the arrow is connected with the electric connector 1 through the power supply cable, and after the power supply on the arrow is activated, the electromagnet assembly 8 is powered through the cable and the electric connector 1, so that the electromagnet assembly 8 works. After the electromagnet assembly 8 is electrified, electromagnetic force is generated, the locking pin 9 is separated from a locking groove on the transmission screw rod 12, the transmission screw rod 12 can move, namely, the servo mechanism drives the spray pipe to move, and the rocket posture is changed.
When in transportation, the power supply on the arrow stops supplying power, namely the electromagnet assembly 8 is powered off, electromagnetic force is not generated any more, and the locking pin 9 is inserted into the locking groove of the transmission screw 12, so that the transmission screw 12 is mechanically limited, and the servo mechanism is locked.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the present utility model. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
It should be noted that the terms "first," "second," and the like in the description and the claims of the present utility model and the above figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate such that embodiments of the utility model described herein may be implemented in sequences other than those illustrated or otherwise described herein.
The above description is only of the preferred embodiments of the present utility model and is not intended to limit the present utility model, but various modifications and variations can be made to the present utility model by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model should be included in the protection scope of the present utility model.
Claims (7)
1. A servo self-locking device, comprising: the device comprises a driving mechanism, an actuating support lug, a locking pin and an electromagnet assembly; the actuating mechanism comprises a transmission screw rod for transmission; one end of the transmission screw rod is in transmission connection with the driving mechanism and is driven by the driving mechanism to rotate; the other end of the transmission screw rod is rotationally connected with the actuating support lug; the transmission screw rod is provided with a locking groove matched with the locking pin; the locking pin is configured to extend into or out of the locking groove under the action of electromagnetic force generated by the electromagnet assembly.
2. The servo self-locking device of claim 1 wherein the actuation mechanism further comprises a housing; the transmission screw rod and the locking pin are both arranged in the housing.
3. The servo self-locking device of claim 2, further comprising a lead screw nut; the screw nut is in threaded connection with the transmission screw; the driving mechanism comprises a power output shaft; the screw nut is fixedly connected with the power output shaft.
4. The servo self-locking device of claim 3, further comprising a bearing for securing said lead screw nut; the bearing sleeve is arranged on the periphery of the screw nut, the bearing inner ring is fixedly connected with the screw nut, and the bearing outer ring is fixedly connected with the housing.
5. The servo self-locking device according to claim 1, wherein a connecting shaft is fixedly arranged at the end part of the transmission screw close to one end of the actuating support lug; the connecting shaft is rotationally connected with the actuating support lug; the rotation axis of the actuating support lug is collinear with the center of the transmission screw.
6. The servo self-locking device of claim 1, further comprising an electrical connector for connecting the electromagnet assembly to an on-arrow power supply.
7. The servo self-locking device of claim 1, further comprising a fixed lug for connecting the servo to the arrow body; the fixed support lugs are hinged with the arrow body through fixed pin shafts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321404717.3U CN219691649U (en) | 2023-06-05 | 2023-06-05 | Servo mechanism self-locking device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321404717.3U CN219691649U (en) | 2023-06-05 | 2023-06-05 | Servo mechanism self-locking device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219691649U true CN219691649U (en) | 2023-09-15 |
Family
ID=87941811
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321404717.3U Active CN219691649U (en) | 2023-06-05 | 2023-06-05 | Servo mechanism self-locking device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219691649U (en) |
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2023
- 2023-06-05 CN CN202321404717.3U patent/CN219691649U/en active Active
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| CP03 | Change of name, title or address |
Address after: No. 1, Haixiang Middle Road, Fengcheng Street, Haiyang City, Yantai City, Shandong Province, 265100 Patentee after: Dongfang space technology (Shandong) Co.,Ltd. Country or region after: China Patentee after: Dongfang Space (Jiangsu) Aerospace Power Co.,Ltd. Patentee after: Oriental space technology (Beijing) Co.,Ltd. Patentee after: Orient Space (Hainan) Technology Co.,Ltd. Address before: No. 1, Haixiang Middle Road, Fengcheng Street, Haiyang City, Yantai City, Shandong Province, 265100 Patentee before: Dongfang space technology (Shandong) Co.,Ltd. Country or region before: China Patentee before: Oriental space technology (Beijing) Co.,Ltd. Patentee before: Dongfang Space (Jiangsu) Aerospace Power Co.,Ltd. Patentee before: Orient Space (Hainan) Technology Co.,Ltd. Address after: No. 1, Haixiang Middle Road, Fengcheng Street, Haiyang City, Yantai City, Shandong Province, 265100 Patentee after: Dongfang space technology (Shandong) Co.,Ltd. Country or region after: China Patentee after: Oriental space technology (Beijing) Co.,Ltd. Patentee after: Dongfang Space (Jiangsu) Aerospace Power Co.,Ltd. Patentee after: Orient Space (Hainan) Technology Co.,Ltd. Address before: No. 1, Haixiang Middle Road, Fengcheng Street, Haiyang City, Yantai City, Shandong Province, 265100 Patentee before: Dongfang space technology (Shandong) Co.,Ltd. Country or region before: China Patentee before: Oriental space technology (Beijing) Co.,Ltd. Patentee before: Oriental space (Xi'an) Aerospace Technology Co.,Ltd. Patentee before: Orient Space (Hainan) Technology Co.,Ltd. |